Missile spiralling mechanism -2

ABSTRACT

A missile  1  with a spiral inducing assembly  2  which is capable of inducing the missile to travel in a continuous spiralling motion without the missile rolling. Two fins  3  and  4  are attached to a tube  5  that is able to rotate around the encircled part of the missile fuselage. The fins  3, 4  are able to rotate in a pivoting manner on the rotatable tube  5  with respect to the rotatable tube  5,  thereby changing their pitch relative to the longitudinal axis of the rotatable tube  5.  Fin  3  is larger than fin  4.  The difference in sizes between the fins makes the larger fin  3  exert a greater force on the rotatable tube  4  than the smaller fin  4  when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube  5  to rotate. When pitched at an angle to the longitudinal axis in unison, both fins  3, 4  would exert a lateral force on the rotatable tube  5.  Thus, as well as forcing the rotatable tube  5  to rotate, the fins  3, 4  would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the missile when in flight.

[0001] The aim of this invention is to provide a missile that has higherchance of surviving attacks from anti-missile weapons when flyingtowards an enemy than missiles currently in use. The missile accordingto this invention is fitted with a mechanism that enables the missile totravel in a continuous spiralling motion while flying towards an enemy,without the need to make continues control adjustments. The mechanism issuch that once activated, the spiralling motion is automatic. Thespiralling motion is achieved during flight without rolling the missile.

[0002] In this invention the spiralling motion of the missile isachieved using moveable fins on a rotatable tube, with the tubeencircling a part of missile (preferrably the forward part of themissile fuselage) and able to rotate around the encircled part of themissile. The fins are attached to the rotatable tube so that they can berotated in a pivoting manner relative to the rotatable tube.

[0003] For the missile to enter a spiralling motion, the fins would needto revolve around part of the missile so that the missile is pushed inchanging directions. In the invention this achieved by using therotatable tube, that allows the fins to revolve around part of themissile—using the rotatable tube as means of travelling around a part ofthe missile. The invention provides a number of means by which rotationof the rotatable tube can be achieved. One way is to use fins that areof unequal size with respect to one another. Having fins that are ofunequal size would cause an aerodynamic imbalance when the fins aremoved from the horizontal position. With one fin pushing harder than theother, rotation of rotatable tube would result. The rotation of therotatable tube would be automatic and continuous while the imbalancebetween the fins was maintained. Placing the fins back in a horizontalposition would remove the imbalance, allowing the rotatable tube to cometo rest. Friction between the missile and the rotatable tube or abraking mechanism such as a hydraulicly activated brake pad being pushagainst the rotatable tube could help to stop the rotatable tube fromrotating.

[0004] Another way of causing the rotatable tube to rotate according tothe invention is to increase the pitch of one fin more than that of theother. Increasing the pitch of one fin relative to the other would causean aerodynamic imbalance on the rotatable tube, thereby forcing it torotate. Allowing the fins to return to a horizontal position wouldremove the aerodynamic imbalance, allowing the rotatable tube to come torest.

[0005]FIG. 1 shows a missile 1 according to this invention, fitted withone form of a spiral inducing assembly 2.

[0006] Referring to FIG. 1, a rotatable tube 3 forming part of thespiral inducing assembly 2 can be seen encircling part of the missilefuselage 4 of the missile 1. The missile fuselage has a fore end and anaft end. Referring to this tube 3 as the primary tube 3, the primarytube 3 is able to rotate around the part of the missile fuselageencircled by the primary tube. The primary tube is shown as beingnarrower in the front than at the rear. Also shown is another tube 5that is fitted to the missile 1 such that it encircles part of themissile fuselage 4 of the missile. Referring to this tube 5 as theactivation tube 5, the activation tube 5 is fitted so that it can bemoved in a forward direction relative to the part of the missilefuselage 4 encircled by the activation tube and then back to itsoriginal position on the missile fuselage. FIG. 1 also shows the edge ofone horizontal fin 6 that is connected to the outside of the primarytube 3. The fin 6 is connected to the outside of primary tube 3 suchthat it can rotate in a pivoting manner as shown in FIG. 2.

[0007]FIG. 1A shows an enlarged illustration of the left side of thespiral inducing assembly 2. The fin 6 in FIG. 1A is connected to theoutside of the primary tube 3 by a connecting joint 7 which is in theform of a connecting rod 7. Extended from the connecting rod 7 in FIG.1A is a protruding section 8 which is used to rotate the connecting rod7. Rotation of the connecting rod 7 causes the fin 6 to rotate in apivoting manner around the connecting rod 7 (in the manner shown in FIG.2). Linked to the protruding section 8 in FIG. 1A is a stem 9. Referringto this stem 9 as an activation stem 9, the activation stem 9 is used asa means for pushing the protruding section 8 such that when theprotruding section 8 is pushed, the protruding section 8 forces theconnecting rod 7 to rotate around the longitudinal axis of theconnecting rod 7. The activation stem 9 is linked to the protrudingsection 8 by a rivet 10. The activation stem 9 is shown as being fittedon the outside of the primary tube 3 and is supported on the primarytube 3 by a retaining bracket 11. The retaining bracket 11 is rigidlyjoined to the primary tube but is channelled to allow the activationstem 9 to move longitudinally between the retaining bracket 11 and theprimary tube 3. The activation stem 9 is allowed to protrude rearwardfrom the primary tube so that it can be reached by the activation tube 5when the activation tube 5 is moved forward on the missile fuselage 4.The activation tube 5 is forced to move forward by an activationmechanism 12 consisting of hydraulic actuators 13 and 14. FIG. 3 showsthe hydraulic actuators 15 and 16 located on the right side of thespiral inducing assembly 2 which also form part of the activationmechanism 12 by which the acivation tube 5 is forced to move. When thehydraulic actuators 13 14 15 and 16 are forced to extend as hydraulicpressure is applied to them, they force the activation tube 5 to moveforward as shown in FIG. 2. FIG. 2 shows that as the activation tube 5is forced to move forward on the missile fuselage 4 when the hydraulicactuators 13 and 14 extend, it eventually makes contact with theactivation stem 9. As the activation tube 5 is forced to move furtherforward, it pushes the activation stem 9 forward on primary tube. As theactivation stem 9 is pushed forward, the activation stem pushes againstthe protruding section 8 and moves the protruding section 8, therebyrotating the fin 6 around the connecting rod 7 in a pivoting manner.

[0008] In FIG. 2 a rivet 10 is shown connecting the activation stem 9 tothe protruding section 9, which allows movement between the activationstem 9 and the protruding section 8. The retaining bracket 11 keeps theactivation stem from moving laterally around the primary tube. Theretaining bracket 11 however does allow longitudinal sliding movement ofthe activation stem 9 so that it can be pushed and moved by theactivation tube 5.

[0009]FIG. 3 shows the the right side of the spiral inducing assembly 2of FIG. 1. Shown is another fin 17, another connecting joint 18 in theform of a connecting rod 18 that connects the fin 17 to the outside ofthe primary tube 3. Another protruding section 19 is used to rotate theconnecting rod 18, and the activation stem 20 is used to push theprotruding section 19, with the activation stem 20 linked to theprotruding section 19 by a rivet 21. Also visible in FIG. 3 is theactivation tube 5. The connecting rod 18 allows the fin 17 to rotate ina pivoting manner. Another retaining bracket 22 is shown supporting therespective activation stem 20.

[0010] Thus, it can be seen from FIGS. 1, 1A, 2 and 3 that theactivation tube 5, the activation stems 9 and 20, retaining brackets 11and 22, protruding sections 8 and 19, rivets 10 and 21 used to connectthe activation stems 9 and 20 to respective protruding sections 8 and19, the connecting joints 7 and 18 in the form of connecting rods 7 and18, and the activation mechanism 12 used to move the activation tube 5consisting of the hydraulic actuators 13, 14, 15 and 16, collectivelyform a fin rotating mechanism.

[0011]FIG. 4 shows the missile 1 of FIG. 1 from underneath. It showsthat one fin 6 is larger than the other fin 17. When these fins 6 and 17are rotated in a pivoting manner and in the same direction to the sameextent, an aerodynamic imbalance between the fins 6 and 17 arises furingflight of the missile because of size diference between the fins 6 and17. The larger fin 6 will exert a greater magnitude of force on theprimary tube 3 during flight of the missile 1 than the smaller fin 17.As a result, the aerodynamic imbalance between the fins 6 and 17 wouldcause the primary tube 3 to rotate. But both fins 16 and 17 would alsobe pushing the missile laterally, in a similar manner to canards. Thus,because the primary tube 3 is forced to rotate, the lateral forceexerted on the missile by the fins 6 and 17 keeps changing, thus forcingthe missile to keep changing its direction and hence entering aspiralling motion.

[0012]FIG. 5 shows the front cut out of the spiral inducing assembly 2of FIG. 1. Shown here is the primary tube 3, the fins 6 and 17, (withfin 6 being larger than fin 17), the missile fuselage 4 of the missile,the activation stems 9 and 20, linked by rivets 10 and 21 to theprotruding sections 8 and 19 respectively, the connecting rods 7 and 18penetrating the primary tube 3, and with the protruding sections 8 and19 screwed in the connecting rods 7 and 18 respectively. FIG. 5 showsthe primary tube 3 as being creased in sections 23, 24 and 25. Thecreased sections 23, 24 and 25 are used as a means to support theprimary tube 3 on the on the encircled part of the missile fuselage 4,while allowing for gaps 26 and 27 to exist between the primary tube 3and the encircled part of the missile fuselage 4. The gaps 26 and 27allow the connecting rods 7 and 18 to protrude inwardly through theprimary tube 3 without making contact with the encircled part of themissile fuselage 4. Securing bolt nuts 28 and 29 are shown securing theconnecting rods 7 and 18 to the primary tube 3, with thrust bearings 30and 31 allowing for easy rotation of the connecting rods 7 and 18 aroundtheir respective longitudinal axes'.

[0013]FIG. 6 shows the rear of the primary tube 3 of FIG. 1 as a cutout. Shown in FIG. 6 are the rear ends of the activation stems 9 and 20,and the retaining brackets 11 and 22 that support the activation stems 9and 20, and prevent uncontrolled lateral movement of the activationstems 9 and 20. The primary tube 3 is shown as having sections creased32, 33 and 34.

[0014] The primary tube can be formed in various geometric shapes,including cylindrical or cone shaped.

[0015]FIG. 7 shows a side cutting of the part of the missile fuselage 35encircled by the primary tube 3 of FIG. 1. The encircled part of themissile fuselage 35 can be seen to be narrower than the rest of themissile fuselage 4. Thrust bearings 36 and 37 are positioned on thenarrowed section of the missile fuselage 35. The thrust bearings areused to support the primary tube and to prevent the primary tube movinglongitudinally relative to the missile fuselage 4.

[0016]FIG. 8 shows another way that the primary tube 3 of FIG. 6 can besupported, with wheels 38, 39 and 40 attached to the creased sections32, 33 and 34 of the primary tube 3. The wheels 38, 39 and 40 help tosupport the primary tube 3 on the encircled part of the missile fuselage35.

[0017]FIG. 9 shows another way of supporting the primary tube 3. Shownis a tube of smaller diameter 41 than the primary tube 3. This smallertube 41 is a supporting tube 41 in that it can be used to support theprimary tube 3. It has a smaller diameter than the primary tube 3 toprovide a gap 42 between the primary tube 3 and the supporting tube 41.The gap 42 is used to allow freedom of movement to the protrudingsections 8 and 19, and the activation stems 9 and 20 shown positionedinside the primary tube 3. The protruding sections 8 and 19 and theconnecting rods 7 and 18 have been formed as moulded units, allowingeasier assembly. Bolts 43, 44, 45 and 46 are used to join the primarytube 3 to the supporting tube 41. The supporting tube 41 is able torotate around the encircled part of the missile fuselage 35.

[0018]FIG. 9A shows a side view of an missile 1 using the fin rotatingmechanism of FIG. 9. The activation stem 9 of FIG. 9 can be seen to beprotruding rearward from inside the primary tube 3.

[0019]FIG. 10 shows a cut out of the front of the primary tube 3 of FIG.1, but with the protruding sections 8 and 19 protruding from the fins 6and 17 respectively.

[0020]FIGS. 11 and 12 show another manner in which the aerodynamicimbalance between the fins can be created during forward flight.

[0021] In FIG. 11 the protruding section 8, on the left side of thespiral inducing assembly 2 is shorter than the protuding section 19 inFIG. 12 on the right side of the spiral inducing assembly 2. The shorterprotruding section 8 would generate a greater degree of movement of fin6 in FIG. 11 than the movement of fin 17 that the protruding section 19would cause in FIG. 12 for an equal movement in the respectiveactivation stems 9 and 20. An aerodynamic imbalance between the finscould thus be created.

[0022]FIGS. 13 and 14 show the left and right sides of the spiralinducing assembly 2 of another arrangement for creating an aerodynamicimbalance between the fins 6 and 17. FIG. 14 shows the activation stem20 on the right side as being shorter than the activation stem 9 on theleft side in FIG. 13. Hence when the activation tube 5 is moved forward,it first starts pushing the activation stem 9 in FIG. 13, forcing fin 6to rotate, and then when the activation tube 5 later starts pushing theactivation stem 20 of FIG. 14, the activation tube 5 will continuepushing the longer activation stem 9 of FIG. 13, forcing the fin 6 inFIG. 13 into a higher degree of rotation, or pitch, than fin 17 of FIG.14, at all times until both fins are allowed to become horizontal againby the activation tube 5 being allowed to retreat.

[0023]FIG. 15 shows a spiral inducing assembly 2 with a wheel 47 fittedto the connecting stem 9. The wheel 47 would reduce frictional forcesbetween the activation stem 9 and the activation tube 5 as theactivation stem travels around the activation tube 5 when the primarytube is rotating.

[0024]FIG. 16 shows the spiral inducing assembly of FIG. 4 with the fins6 and 17 of FIG. 4, and with the primary tube 3 in a state of rotation.It can be seen comparing FIG. 4 with FIG. 16 how the lateral forces onthe missile would be constantly changing, enabling the spiral inducingassembly 2, to force the missile 1 to travel in a continuous spirallingmotion.

[0025] Looking at the fins 6 and 17 shown in FIG. 16 it can be seen thatthe rear section of each fin behind the respective connecting rods 7 and18 is greater than the section of each fin in front the respectiveconnecting rods 7 and 18. This is deliberate. This is used to allow thefins to adopt a horizontal position when hydraulic pressure is notapplied to the hydraulic actuators 13, 14 (and 15 and 16 of FIG. 3).Aerodynamic forces are in effect used to allow the fins to remain aresting horizontal position thereby allowing non-spiralling flight.Friction between activation the activation tube 5 and activation stems 9and 20 caused by the rotation of the activation stems 9 and 20 aroundthe activation tube (since the activation stems rotate with the primarytube) can be used as a means of slowing the rotation of the primary tubewhen smooth flight is desired. The braking mechanisms shown in FIGS. 17and 18 could also be used as a means of slowing the primary tube whensmooth flight needs to be resumed.

[0026]FIG. 17 shows a side cutting of the primary tube 3 and the part ofthe missile fuselage 35 encircled by the primary tube 3. Shown here is ahydraulic actuator 48 attached to the encircled part of the missilefuselage 35, in an extended form. Extended it creates friction on theprimary tube 3 and acts as a brake to help slow the primary tube 3 whenthe spiral inducing assembly is de-activated. Using a braking systemlightly would allow the primary tube 3 to rotate, but would intensifythe lateral forces on the missile 1. To allow use of a brakingmechanism, the primary tube 3 would be kept smooth and round in the areathat fricion is induced. Any creased sections 23, 24, 32, 34 would berestricted to areas where the hydraulic actuator 48 would not makecontact.

[0027]FIG. 17A shows the hydraulic actuator rod 48 in a compressedstate, as when the primary tube 3 is allowed to freely rotate.

[0028]FIG. 18 shows another braking mechanism where a lever is used toslow the primary tube. The lever 49 is shown protruding from a hole 50in the missile fuselage, and is operated by an actuator in the form ofan electric motor 51.

[0029]FIG. 19 shows a spiral inducing assembly 2 where the primary tube3 extends over the activation tube 5, but the fin is located on theoutside of the primary tube.

The claims defining this invention are as follows:
 1. A missilecomprising a missile fuselage and a spiral inducing assembly, which saidspiral inducing assembly is capable of forcing the missile to travel ina spiralling motion during flight of the missile, and which said spiralinducing assembly consists of a tube, and which said tube encircles partof the missile fuselage of the missile and is able to rotate relative tothe encircled part of the missile fuselage, with a plurality of finsconnected to the said tube, which said fins are connected to the tubesuch that the fins protrude laterally outward from the tube and suchthat the said fins can be rotated in a pivoting manner relative to thetube, and such that the said fins can be rotated in the said pivotingmanner in the same direction, and which said spiral inducing assemblycomprises a fin rotating mechanism by which fin rotating mechanism thesaid fins can be rotated in the said pivoting manner, and by which saidfin rotating mechanism the said fins can be rotated in the said pivotingmanner and simultaneously in the same direction as each other such thatduring flight of the missile one of the said fins connected to the tubecan continuously exert a greater magnitude of force on the said tubethan can another of the said fins that is connected to the said tube. 2.A missile comprising a missile fuselage and a spiral inducing assembly,which said spiral inducing assembly is capable of forcing the missile totravel in a spiralling motion during flight of the said missile, andwhich said spiral inducing assembly consists of a tube, and which saidtube encircles part of the missile fuselage of the missile and is ableto rotate relative to the encircled part of the missile fuselage, with aplurality of fins connected to the said tube, which said fins areconnected to the tube such that the fins protrude laterally outward fromthe tube and such that the said fins can be rotated in a pivoting mannerrelative to the tube, and which said spiral inducing assembly comprisesa fin rotating mechanism by which fin rotating mechanism the said finscan be rotated in the said pivoting manner such that during flight ofthe said missile one of the said fins connected to the tube cancontinuously exert a greater magnitude of force on the said tube thancan another of the said fins that is connected to the said tube.
 3. Amissile comprising a missile fuselage and a spiral inducing assembly,which said spiral inducing assembly is capable of forcing the missile totravel in a spiralling motion during flight of the missile, and whichsaid spiral inducing assembly consists of a tube, and which said tubeencircles part of the missile fuselage of the missile and is able torotate relative to the encircled part of the missile fuselage, with aplurality of fins connected to the said tube, which said fins areconnected to the tube such that the fins protrude laterally outward fromthe tube and such that the said fins can be rotated in a pivoting mannerrelative to the tube, and such that the said fins can be rotated in thesaid pivoting manner in the same direction, and which said spiralinducing assembly comprises a fin rotating mechanism by which said finrotating mechanism the said fins can be rotated in the said pivotingmanner and in the same direction as each other and by which said finrotating mechanism the said fins thus can be rotated in the said samedirection relative to the tube such that one of the said fins connectedto the tube can be rotated to a greater degree relative to the tube thancan another of the said fins that is connected to the said tube.
 4. Amissile comprising a missile fuselage and a spiral inducing assembly,which said spiral inducing assembly is capable of forcing the missile totravel in a spiralling motion during flight of the said missile andwhich said spiral inducing assembly consists of a tube, and which saidtube encircles part of the missile fuselage of the missile and is ableto rotate relative to the encircled part of the missile fuselage, with aplurality of fins connected to the said tube, which said fins areconnected to the tube such that the fins protrude laterally outward fromthe tube and such that the said fins can be rotated in a pivoting mannerrelative to the tube, and such that the said fins can be rotated in thesaid pivoting manner in the same direction, and which said spiralinducing assembly comprises a fin rotating mechanism by which said finrotating mechanism the said fins can be rotated in the said pivotingmanner and in the same direction as each other, and with the said finsbeing such that one of said fins connected to the tube is of larger sizethan is another of the said fins.
 5. The missile of claim 1 wherein thesaid fin that is able to exert a greater magnitude of force on the tubecan be pivotly rotated to a greater degree than the said other fin bymeans of the fin rotating mechanism, such that when the said fin thatcan be rotated to greater degree is rotated to a greater degree than thesaid other fin the fin that is rotated to a greater degree exerts agreater magnitude of force on the tube during flight of the missile thanthe said other fin.
 6. The missile of claim 1 wherein the said fin thatis able to exert a greater magnitude of force on the tube is of largersize than the said other fin such that by being of larger size the finthat is of larger size can exert a greater magnitude of force on thetube than the said other fin during flight of the missile.
 7. Themissile of claim 2 wherein the said fin that is able to exert a greatermagnitude of force on the tube can be pivotly rotated to a greaterdegree than the other said fin by means of the fin rotating mechanism,such that when the said fin that can be rotated to greater degree isrotated to a greater degree than the said other fin the fin that isrotated to a greater degree exerts a greater magnitude of force on thetube during flight of the missile than the said other fin.
 8. Themissile of claim 2 wherein the said fin that is able to exert a greatermagnitude of force on the tube is of larger size than the said other finsuch that by being of larger size the fin that is of larger size canexert a greater magnitude of force on the tube than the said other finduring flight of the missile.
 9. A missile comprising a missile fuselageand a spiral inducing assembly, which said spiral inducing assembly iscapable of forcing the missile to travel in a spiralling motion duringflight of the said missile, and which said spiral inducing assemblyconsists of a tube, and which said tube encircles part of the missilefuselage of the missile and is able to rotate relative to the encircledpart of the missile fuselage, with a plurality of fins connected to thesaid tube, which said fins are connected to the tube such that the finsprotrude laterally outward from the tube and such that the said fins canbe rotated in a pivoting manner relative to the tube, and such that thesaid fins can be rotated in the said pivoting manner in the samedirection and in unison relative to the tube and which said spiralinducing assembly comprises a fin rotating mechanism by which said finrotating mechanism the said fins can be rotated in the said pivotingmanner in the same direction as each other and in unison relative to thetube and with the said fins being such that during flight of the saidmissile one of the said fins connected to the tube can continuouslyexert a greater magnitude of force on the said tube than can another ofthe said fins that is connected to the said tube.
 10. The missile ofclaim 9 wherein the said fin that is able to exert a greater magnitudeof force on the tube is of larger size than the said other fin such thatby being of larger size the fin that is of larger size can exert agreater magnitude of force on the tube than the said other fin duringflight of the missile.
 11. The missile of claim 1 wherein the spiralinducing assembly can force the said missile to travel in a continuousspiralling motion while the said fins are continuously maintained in arigid position with respect to the said tube.
 12. A missile comprising amissile fuselage and a spiral inducing assembly, which said spiralinducing assembly is capable of forcing the missile to travel in aspiralling motion during flight of the said missile, and which saidspiral inducing assembly consists of a tube, which said tube encirclespart of the missile fuselage of the missle and which said tube is ableto rotate relative to the encircled part of the missile fuselage, with aplurality of fins connected to the said tube, which said fins areconnected to the tube such that the fins protrude laterally outward fromthe tube and such that the said fins can be rotated in a pivoting mannerrelative to the tube, and such that the said fins can be rotated in thesaid pivoting manner in the same direction, with a stem connected to onefin and another stem connected to another fin, and with an additionaltube encircling part of the missile fuselage of the missile, whichmissile fuselage comprises a fore end and an aft end, and which saidadditional tube is able to move between the fore end and the aft end ofthe missile fuselage, with at least one hydraulic actuator connected tothe missile fuselage, which hydraulic actuator is connected to themissile fuselage such that the hydraulic actuator is able to push theadditional tube and force the additional tube to move between the foreend and the aft end of the missile fuselage, such that as the additionaltube is moved the additional tube can be pressed against the said stems,such that as the additional tube presses against the stems, therespective fins are rotated in a pivoting manner with respect to thetube that is able to rotate relative to the missile fuselage, with thestems of such relative lengths with respect to one another and with thestems connected to the respective fins such that the said fins can berotated in the said pivoting manner and in the same direction as eachother such that one of the said fins can be pivotly rotated to a greaterdegree relative to the tube that is able to rotate relative to themissile fuselage than can another of the said fins be rotated relativeto tube that is able to rotate relative to the missile fuselage.
 13. Themissile of claim 12 wherein the said stems are positioned such that theyextend longitudinally with respect to the missile fuselage of themissile.
 14. The missile of claim 12 wherein the additional tube is inthe form of a ring.
 15. The missile of claim 12 wherein an additionalhydraulic actuator is connected to the missile fuselage, whichadditional hydraulic actuator is connected to the missile fuselage suchthat as hydraulic pressure is applied to the additional hydraulicactuator, the additional hydraulic actuator is able to be pressedagainst the tube that is able to rotate around the missile fuselage suchthat friction can be induced between the additional hydraulic actuatorand the tube that is able to rotate around the missile fuselage.
 16. Themissile of claim 12 wherein a lever is connected to the missilefuselage, which lever is connected to the missile fuselage such that thelever is able to be pressed against the tube that is able to rotatearound the missile fuselage such that friction can be induced betweenthe lever and the tube that is able to rotate around the missilefuselage.
 17. The missile of claim 1 wherein an additional hydraulicactuator is connected to the missile fuselage, which additionalhydraulic actuator is connected to the missile fuselage such that ashydraulic pressure is applied to the additional hydraulic actuator, theadditional hydraulic actuator is able to be pressed against the tubethat is able to rotate around the missile fuselage such that frictioncan be induced between the additional hydraulic actuator and the tubethat is able to rotate around the missile fuselage.
 18. The missile ofclaim 1 wherein a lever is connected to the missile fuselage, whichlever is connected to the missile fuselage such that the lever is ableto be pressed against the tube that is able to rotate around the missilefuselage such that friction can be induced between the lever and thetube that is able to rotate around the missile fuselage.
 19. The missileof claim 2 wherein an additional hydraulic actuator is connected to themissile fuselage, which additional hydraulic actuator is connected tothe missile fuselage such that as hydraulic pressure is applied to theadditional hydraulic actuator, the additional hydraulic actuator is ableto be pressed against the tube that is able to rotate around the missilefuselage such that friction can be induced between the additionalhydraulic actuator and the tube that is able to rotate around themissile fuselage.
 20. The missile of claim 2 wherein a lever isconnected to the missile fuselage, which lever is connected to themissile fuselage such that the lever is able to be pressed against thetube that is able to rotate around the missile fuselage such thatfriction can be induced between the lever and the tube that is able torotate around the missile fuselage.
 21. The missile of claim 3 whereinan additional hydraulic actuator is connected to the missile fuselage,which additional hydraulic actuator is connected to the missile fuselagesuch that as hydraulic pressure is applied to the additional hydraulicactuator, the additional hydraulic actuator is able to be pressedagainst the tube that is able to rotate around the missile fuselage suchthat friction can be induced between the additional hydraulic actuatorand the tube that is able to rotate around the missile fuselage.
 22. Themissile of claim 3 wherein a lever is connected to the missile fuselage,which lever is connected to the missile fuselage such that the lever isable to be pressed against the tube that is able to rotate around themissile fuselage such that friction can be induced between the lever andthe tube that is able to rotate around the missile fuselage.
 23. Themissile of claim 4 wherein an additional hydraulic actuator is connectedto the missile fuselage, which additional hydraulic actuator isconnected to the missile fuselage such that as hydraulic pressure isapplied to the additional hydraulic actuator, the additional hydraulicactuator is able to be pressed against the tube that is able to rotatearound the missile fuselage such that friction can be induced betweenthe additional hydraulic actuator and the tube that is able to rotatearound the missile fuselage.
 24. The missile of claim 4 wherein a leveris connected to the missile fuselage, which lever is connected to themissile fuselage such that the lever is able to be pressed against thetube that is able to rotate around the missile fuselage such thatfriction can be induced between the lever and the tube that is able torotate around the missile fuselage.
 25. The missile of claim 9 whereinan additional hydraulic actuator is connected to the missile fuselage,which additional hydraulic actuator is connected to the missile fuselagesuch that as hydraulic pressure is applied to the additional hydraulicactuator, the additional hydraulic actuator is able to be pressedagainst the tube that is able to rotate around the missile fuselage suchthat friction can be induced between the additional hydraulic actuatorand the tube that is able to rotate around the missile fuselage.
 26. Themissile of claim 9 wherein a lever is connected to the missile fuselage,which lever is connected to the missile fuselage such that the lever isable to be pressed against the tube that is able to rotate around themissile fuselage such that friction can be induced between the lever andthe tube that is able to rotate around the missile fuselage.